Turbine engine assembly including a rotating detonation combustor

ABSTRACT

A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture. The rotating detonation combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit extending along at least one of the radially inner side wall or the radially outer side wall. The assembly also includes a first compressor configured to discharge a flow of cooling air towards the rotating detonation combustor, and to channel the flow of cooling air through the cooling conduit.

BACKGROUND

The present disclosure relates generally to rotating detonationcombustion systems and, more specifically, to systems and methods ofcooling a rotating detonation combustor.

In rotating detonation engines and, more specifically, in rotatingdetonation combustors, a mixture of fuel and an oxidizer is ignited suchthat combustion products are formed. For example, the combustion processbegins when the fuel-oxidizer mixture in a tube or a pipe structure isignited via a spark or another suitable ignition source to generate acompression wave. The compression wave is followed by a chemicalreaction that transitions the compression wave to a detonation wave. Thedetonation wave enters a combustion chamber of the rotating detonationcombustor and travels along the combustion chamber. Air and fuel areseparately fed into the rotating detonation combustion chamber and areconsumed by the detonation wave. As the detonation wave consumes air andfuel, combustion products traveling along the combustion chamberaccelerate and are discharged from the combustion chamber. However,rotating detonation combustors generally operate at high localcombustion temperatures greater than the temperature limit of materialsused to form at least some portions of the rotating detonationcombustor.

BRIEF DESCRIPTION

In one aspect, a turbine engine assembly is provided. The assemblyincludes a rotating detonation combustor configured to combust afuel-air mixture. The rotating detonation combustor includes a radiallyinner side wall, a radially outer side wall extending about the radiallyinner side wall such that an annular combustion chamber is at leastpartially defined therebetween, and a cooling conduit extending along atleast one of the radially inner side wall or the radially outer sidewall. The assembly also includes a first compressor configured todischarge a flow of cooling air towards the rotating detonationcombustor, and to channel the flow of cooling air through the coolingconduit.

In another aspect, a rotating detonation combustor is provided. Thecombustor includes a radially inner side wall, a radially outer sidewall extending about the radially inner side wall such that an annularcombustion chamber is at least partially defined therebetween, and acooling conduit configured to channel cooling air therethrough. Thecooling conduit extends along at least one of the radially inner sidewall or the radially outer side wall.

In yet another aspect, a turbine engine assembly is provided. Theassembly includes a rotating detonation combustor configured to combusta fuel-air mixture. The rotating detonation combustor includes aradially inner side wall, a radially outer side wall extending about theradially inner side wall such that an annular combustion chamber is atleast partially defined therebetween, and a cooling conduit extendingalong at least one of the radially inner side wall or the radially outerside wall. The assembly further includes a source of cooling fluidcoupled in flow communication with the rotating detonation combustor.The source of cooling fluid is configured to discharge a flow of coolingfluid towards the rotating detonation combustor, and to channel the flowof cooling fluid through the cooling conduit. The cooling fluid includesat least one of steam, water, or fuel.

DRAWINGS

These and other features, aspects, and advantages of the presentdisclosure will become better understood when the following detaileddescription is read with reference to the accompanying drawings in whichlike characters represent like parts throughout the drawings, wherein:

FIG. 1 is a schematic illustration of an exemplary combined cycle powergeneration system;

FIG. 2 is a schematic illustration of an exemplary rotating detonationcombustor that may be used in the gas turbine engine assembly shown inFIG. 1;

FIG. 3 is a schematic illustration of the rotating detonation combustorshown in FIG. 2, in accordance with a second embodiment of thedisclosure;

FIG. 4 is an enlarged cross-sectional view of a portion of the rotatingdetonation combustor shown in FIG. 2, taken along Area 4;

FIG. 5 is an enlarged cross-sectional view of a portion of the rotatingdetonation combustor shown in FIG. 2, taken along Area 5;

FIG. 6 is a schematic illustration of an exemplary rotating detonationcombustion system that may be used in the combined cycle powergeneration system shown in FIG. 1;

FIG. 7 is a schematic illustration of an alternative rotating detonationcombustion system that may be used in the combined cycle powergeneration system shown in FIG. 1;

FIG. 8 is an enlarged cross-sectional view of a portion of the rotatingdetonation combustor shown in FIG. 7, taken along Area 8; and

FIG. 9 is a further alternative rotating detonation combustion systemthat may be used in the combined cycle power generation system shown inFIG. 1.

Unless otherwise indicated, the drawings provided herein are meant toillustrate features of embodiments of the disclosure. These features arebelieved to be applicable in a wide variety of systems comprising one ormore embodiments of the disclosure. As such, the drawings are not meantto include all conventional features known by those of ordinary skill inthe art to be required for the practice of the embodiments disclosedherein.

DETAILED DESCRIPTION

In the following specification and the claims, reference will be made toa number of terms, which shall be defined to have the followingmeanings.

The singular forms “a”, “an”, and “the” include plural references unlessthe context clearly dictates otherwise.

“Optional” or “optionally” means that the subsequently described eventor circumstance may or may not occur, and that the description includesinstances where the event occurs and instances where it does not.

Approximating language, as used herein throughout the specification andclaims, may be applied to modify any quantitative representation thatcould permissibly vary without resulting in a change in the basicfunction to which it is related. Accordingly, a value modified by a termor terms, such as “about”, “approximately”, and “substantially”, are notto be limited to the precise value specified. In at least someinstances, the approximating language may correspond to the precision ofan instrument for measuring the value. Here and throughout thespecification and claims, range limitations may be combined and/orinterchanged. Such ranges are identified and include all the sub-rangescontained therein unless context or language indicates otherwise.

Embodiments of the present disclosure relate to systems and methods ofcooling a rotating detonation combustor. More specifically, the systemsdescribed herein include a rotating detonation combustor including anannular combustion chamber defined by a radially inner side wall and aradially outer side wall, and at least one cooling conduit positionedfor cooling one or both of the radially inner side wall or the radiallyouter side wall. The cooling conduit described herein cools the sidewalls by channeling a cooling fluid therethrough, such as cooling air(i.e., an oxidizer), fuel, steam, or water. As such, the rotatingdetonation combustor described herein is capable of producingdetonations while still operating within predefined material temperaturelimits.

As used herein, “detonation” and “quasi-detonation” may be usedinterchangeably. Typical embodiments of detonation chambers include ameans of igniting a fuel/oxidizer mixture, for example a fuel/airmixture, and a confining chamber, in which pressure wave frontsinitiated by the ignition process coalesce to produce a detonation wave.Each detonation or quasi-detonation is initiated either by externalignition, such as spark discharge or laser pulse, or by gas dynamicprocesses, such as shock focusing, autoignition or by another detonationvia cross-firing. The geometry of the detonation chamber is such thatthe pressure rise of the detonation wave expels combustion products outthe detonation chamber exhaust to produce a thrust force. In addition,rotating detonation combustors are designed such that a substantiallycontinuous detonation wave is produced and discharged therefrom. Asknown to those skilled in the art, detonation may be accomplished in anumber of types of detonation chambers, including detonation tubes,shock tubes, resonating detonation cavities, and annular detonationchambers.

FIG. 1 is a schematic illustration of an exemplary combined cycle powergeneration system 100. Power generation system 100 includes a gasturbine engine assembly 102 and a steam turbine engine assembly 104. Gasturbine engine assembly 102 includes a compressor 106, a combustor 108,and a first turbine 110 powered by expanding hot gas produced incombustor 108 for driving an electrical generator 112. Gas turbineengine assembly 102 may be used in a stand-alone simple cycleconfiguration for power generation or mechanical drive applications. Inthe exemplary embodiment, exhaust gas 114 is channeled from firstturbine 110 towards a heat recovery steam generator (HRSG) 116 forrecovering waste heat from exhaust gas 114. More specifically, HRSG 116transfers heat from exhaust gas 114 to water/steam 118 channeled throughHRSG 116 to produce steam 120. Steam turbine engine assembly 104includes a second turbine 122 that receives steam 120, which powerssecond turbine 122 for further driving electrical generator 112.

In operation, air enters gas turbine engine assembly 102 through anintake 121 and is channeled through multiple stages of compressor 106towards combustor 108. Compressor 106 compresses the air and the highlycompressed air is channeled from compressor 106 towards combustor 108and mixed with fuel. The fuel-air mixture is combusted within combustor108. High temperature combustion gas generated by combustor 108 ischanneled towards first turbine 110. Exhaust gas 114 is subsequentlydischarged from first turbine 110 through an exhaust 123.

FIG. 2 is a schematic illustration of an exemplary rotating detonationcombustor 124 that may be used in gas turbine engine assembly 102 (shownin FIG. 1). In the exemplary embodiment, rotating detonation combustor124 (i.e., combustor 108 (shown in FIG. 1)) includes a radially outerside wall 126 and a radially inner side wall 128 that both extendcircumferentially relative to a centerline 130 of rotating detonationcombustor 124. As such, an annular combustion chamber 132 is definedbetween radially outer side wall 126 and radially inner side wall 128.In addition, rotating detonation combustor 124 includes a fuel-air mixer134 coupled within annular combustion chamber 132. Fuel-air mixer 134receives fuel 136 and air (not shown), and rotating detonation combustor124 combusts a fuel-air mixture 138 discharged from fuel-air mixer 134.Moreover, rotating detonation combustor 124 channels fuel-air mixture138 in a first direction 140 within annular combustion chamber 132.While shown as traveling in an axial direction along the length ofrotating detonation combustor 124, it should be understood that fuel-airmixture 138 also flows helically within annular combustion chamber 132.

In further embodiments, annular combustion chamber 132 is any suitablegeometric shape and does not necessarily include an inner liner and/orcenter body. For example, in some embodiments, annular combustionchamber 132 is substantially cylindrical.

Rotating detonation combustor 124 further includes a cooling conduit 142extending along at least one of radially outer side wall 126 or radiallyinner side wall 128. For example, rotating detonation combustor 124includes at least one annular jacket radially spaced from at least oneof radially outer side wall 126 or radially inner side wall 128 for atleast partially defining cooling conduit 142. More specifically, in oneembodiment, a first annular jacket 144 is spaced from radially outerside wall 126 such that a first cooling conduit 146 is defined betweenradially outer side wall 126 and first annular jacket 144. In addition,a second annular jacket 148 is spaced from radially inner side wall 128such that a second cooling conduit 150 is defined between radially innerside wall 128 and second annular jacket 148. In an alternativeembodiment, and as applicable to the other embodiments described herein,cooling is provided to either radially outer side wall 126 or radiallyinner side wall 128, but not both, with a single cooling conduit.

In the exemplary embodiment, compressor 106 (shown in FIG. 1) dischargesa flow of cooling air 152 towards rotating detonation combustor 124 suchthat the flow of cooling air 152 is channeled through cooling conduits142. As such, heat produced by the combustion of fuel-air mixture 138 isconducted through radially outer side wall 126 and radially inner sidewall 128, and transferred to cooling air 152 channeled through coolingconduits 142. In one embodiment, compressor 106 is coupled in flowcommunication with rotating detonation combustor 124 such that the flowof cooling air 152 is channeled within first cooling conduit 146 andsecond cooling conduit 150 in a second direction 154 opposite from firstdirection 140. In addition, first cooling conduit 146 and second coolingconduit 150 are oriented such that the flow of cooling air 152 channeledtherethrough is further channeled towards fuel-air mixer 134 such thatfuel-air mixture 138 is formed from cooling air 152. In other words,first cooling conduit 146 and second cooling conduit 150 are orientedsuch that the flow of cooling air 152 is channeled in a direction thatenables cooling air 152 to be combined with fuel 136 and included infuel-air mixture 138. More specifically, cooling air 152 enters rotatingdetonation combustor 124 at a first end 153 thereof, and flows in seconddirection 154 towards towards a second end 155 of rotating detonationcombustor 124. Cooling air 152 is then injected into annular combustionchamber 132 for mixing with fuel 136.

Moreover, in one embodiment, cooling conduits 142 and fuel-air mixer 134are coupled in flow communication such that the air in fuel-air mixture138 is derived entirely from the flow of cooling air 152, and such thatno air from compressor 106 bypasses annular combustion chamber 132. Assuch, limiting airflow bypass facilitates enhancing the pressure gaincapability of rotating detonation combustor 124 such that the efficiencyof gas turbine engine 102 is increased.

Rotating detonation combustor 124 further includes a first end plate 156and a second end plate 158. First end plate 156 is coupled to radiallyouter side wall 126 and radially inner side wall 128 such that annularcombustion chamber 132 is at least partially defined by first end plate156. First end plate 156 includes an air inlet 160 defined therein. Airinlet 160 is positioned to couple cooling conduits 142 in flowcommunication with annular combustion chamber 132 upstream of fuel-airmixer 134. Second end plate 158 is spaced from first end plate 156 suchthat cooling conduits 142 are at least partially defined therefrom. Assuch, cooling air 152 channeled through first cooling conduit 146 andsecond cooling conduit 150 is channeled towards air inlet 160 forinjection into annular combustion chamber 132 and for mixing with fuel136 to form fuel-air mixture 138.

FIG. 3 is a schematic illustration of rotating detonation combustor 124in accordance with a second embodiment of the disclosure. As describedabove, rotating detonation combustor 124 channels fuel-air mixture 138in first direction 140 within annular combustion chamber 132. In theexemplary embodiment, second cooling conduit 150 extends along radiallyinner side wall 128, and compressor 106 (shown in FIG. 1) is coupled inflow communication with rotating detonation combustor 124 such that theflow of cooling air 152 within second cooling conduit 150 is likewisechanneled in first direction 140 for discharge towards first turbine 110(shown in FIG. 1). In such an embodiment, the air in fuel-air mixture138 is derived entirely from the flow of cooling air 152 channeledthrough first cooling conduit 146. As such, channeling cooling air 152in first direction 140 provides cooling along radially inner side wall128 and provides purging and pilot flame holding capabilities forrotating detonation combustor 124.

FIG. 4 is an enlarged cross-sectional view of a portion of rotatingdetonation combustor 124, taken along Area 4 (shown in FIG. 2). In theexemplary embodiment, rotating detonation combustor 124 further includesa plurality of thermally conductive projection members 162 extendinginto an interior 164 of first cooling conduit 146. Thermally conductiveprojection member 162 provides a heat sink for heat produced bycombustion of fuel-air mixture 138 (shown in FIG. 2) and conductedthrough radially outer side wall 126. As such, heat dissipation fromradially outer side wall 126 is improved. As shown, thermally conductiveprojection members 162 extend into interior 164 of first cooling conduit146 from radially outer side wall 126. Alternatively, or in addition tothermally conductive projection members 162 extending from radiallyouter side wall 126, thermally conductive projection members 162 extendinto second cooling conduit 150 from radially inner side wall 128 (bothshown in FIG. 2). In addition, thermally conductive projection member162 acts as a turbulator to facilitate vitiating the flow of cooling air152 channeled across radially outer side wall 126, thereby increasingheat transfer to cooling air 152.

FIG. 5 is an enlarged cross-sectional view of a portion of rotatingdetonation combustor 124, taken along Area 5 (shown in FIG. 2). In theexemplary embodiment, cooling conduit 142 extends within a thicknessportion of at least one of radially outer side wall 126 or radiallyinner side wall 128. As shown, cooling conduit 142 extends within thethickness portion of radially outer side wall 126. In addition, at leasta portion of radially outer side wall 126 is recessed relative to aninterior 166 of annular combustion chamber 132 such that one or morestepped side wall portions 168 are formed. Each stepped side wallportion 168 defines an air pocket 170 within annular combustion chamber132, and includes an opening 172 defined therein that couples coolingconduit 142 in flow communication with air pocket 170. As such, at leasta portion of cooling air 152 channeled within cooling conduit 142 flowsinto air pocket 170, thereby forming an air isolation layer 174 withinannular combustion chamber 132. As such, air isolation layer 174provides cooling and pressure force dampening, induced by detonativecombustion, for radially outer side wall 126.

FIG. 6 is a schematic illustration of an exemplary rotating detonationcombustion (RDC) system 176 that may be used in combined cycle powergeneration system 100 (shown in FIG. 1). In the exemplary embodiment,RDC system 176 includes rotating detonation combustor 124 and a source178 of cooling fluid, such as steam or water 180. Source 178 of coolingfluid channels cooling fluid, such as steam or water 180, towardsrotating detonation combustor 124, and channels the flow of coolingfluid through cooling conduits 142. As such, heat produced by thecombustion of fuel-air mixture 138 is transferred to steam or water 180such that heated steam or water 182 is formed. Rotating detonationcombustor 124 then channels a flow of heated steam or water 182 fromcooling conduits 142 towards second turbine 122 (shown in FIG. 1) foruse in the bottoming cycle thereof to facilitate power generation. Assuch, cooling is provided to rotating detonation combustor 124 and heatproduced by the combustion of fuel-air mixture 138 is utilized in aneffective and thermally efficient manner.

FIG. 7 is a schematic illustration of an alternative RDC system 184 thatmay be used in combined cycle power generation system 100 (shown in FIG.1), and FIG. 8 is an enlarged cross-sectional view of a portion ofrotating detonation combustor 124, taken along Area 8 (shown in FIG. 7).In the exemplary embodiment, RDC system 184 includes rotating detonationcombustor 124 and a source 186 of cooling fluid, such as fuel 136. Inoperation, source 186 of cooling fluid channels fuel 136 through coolingconduits 142.

In addition, referring to FIG. 8, radially outer side wall 126 includesat least one fuel inlet 188 defined therein. Specifically, a pluralityof fuel inlets 188 are spaced axially from each other relative tocenterline 130 (shown in FIG. 2) of rotating detonation combustor 124.Fuel inlets 188 inject fuel 136, in the form of fuel jets 190, intoannular combustion chamber 132 for mixing with fuel-air mixture 138.Moreover, rotating detonation combustor 124 includes fuel-air mixer 134,and fuel-air mixer 134 is positioned within annular combustion chamber132 upstream from the plurality of fuel inlets 188 relative to a flowdirection of fuel-air mixture 138. As such, staged fuel injectionlongitudinally relative to centerline 130 (shown in FIG. 2) facilitatesimproving mixing of the fuel and air, and facilitates controlling theequivalence ratio of the fuel-air mixture along the axial length ofrotating detonation combustor 124. Moreover, staged fuel injection alsofacilitates improving the fill length of rotating detonation combustor124.

FIG. 9 is a further alternative RDC system 192 that may be used incombined cycle power generation system 100 (shown in FIG. 1). In theexemplary embodiment, RDC system 192 includes a second compressor 194coupled downstream from and that receives a flow of bleed air 196 fromcompressor 106. Second compressor 194 compresses the flow of bleed air196, and discharges a flow of boosted cooling air 198 towards rotatingdetonation combustor 124 such that fuel-air mixture 138 (shown in FIG.2) is formed from a mixed flow of cooling air 152 (shown in FIG. 2) andboosted cooling air 198. As such, using boosted cooling air 198 to coolrotating detonation combustor 124 facilitates improving the coolingeffectiveness provided to rotating detonation combustor 124 from thecooling fluid.

In some embodiments, RDC system 192 includes a cooling device 200positioned between compressor 106 and second compressor 194. Coolingdevice 200 cools the flow of bleed air 196 before being channeledtowards second compressor 194. As such, compression of bleed air 196within second compressor 194 is provided in a more cost effective mannerrelative to compressing uncooled air.

The systems and methods described herein facilitate providing cooling toa rotating detonation combustor. The cooling is provided by channeling acooling fluid through one or more cooling conduits that extend along aradially outer side wall or a radially inner side wall of the rotatingdetonation combustor. In addition, the system described hereinfacilitates using the heat generated by combustion to improve thethermal efficiency of related assemblies.

An exemplary technical effect of the systems and methods describedherein includes at least one of: (a) providing cooling to a rotatingdetonation combustor; (b) increasing the efficiency of a gas turbineengine; and (c) utilizing one or more architectural cooling concepts toimprove the thermal efficiency of a turbine engine assembly.

Exemplary embodiments of RDC systems are provided herein. The systemsand methods are not limited to the specific embodiments describedherein, but rather, components of systems and/or steps of the methodsmay be utilized independently and separately from other componentsand/or steps described herein. For example, the configuration ofcomponents described herein may also be used in combination with otherprocesses, and is not limited to practice with only ground-based,combined cycle power generation systems, as described herein. Rather,the exemplary embodiment can be implemented and utilized in connectionwith many applications where a RDC system may be implemented.

Although specific features of various embodiments of the presentdisclosure may be shown in some drawings and not in others, this is forconvenience only. In accordance with the principles of embodiments ofthe present disclosure, any feature of a drawing may be referencedand/or claimed in combination with any feature of any other drawing.

This written description uses examples to disclose the embodiments ofthe present disclosure, including the best mode, and also to enable anyperson skilled in the art to practice embodiments of the presentdisclosure, including making and using any devices or systems andperforming any incorporated methods. The patentable scope of theembodiments described herein is defined by the claims, and may includeother examples that occur to those skilled in the art. Such otherexamples are intended to be within the scope of the claims if they havestructural elements that do not differ from the literal language of theclaims, or if they include equivalent structural elements withinsubstantial differences from the literal languages of the claims.

What is claimed is:
 1. A turbine engine assembly comprising: a rotatingdetonation combustor configured to combust a fuel-air mixture, whereinsaid rotating detonation combustor comprises: a radially inner sidewall; a radially outer side wall extending about said radially innerside wall such that an annular combustion chamber is at least partiallydefined therebetween; and a cooling conduit extending along at least oneof said radially inner side wall or said radially outer side wall; and afirst compressor configured to discharge a flow of cooling air towardssaid rotating detonation combustor and configured to channel the flow ofcooling air through said cooling conduit.
 2. The turbine engine assemblyin accordance with claim 1, wherein said rotating detonation combustorfurther comprises an annular jacket radially spaced from at least one ofsaid radially inner side wall or said radially outer side wall, saidannular jacket at least partially defining said cooling conduit.
 3. Theturbine engine assembly in accordance with claim 1, wherein saidrotating detonation combustor is configured to channel the fuel-airmixture in a first direction within said annular combustion chamber,said first compressor coupled in flow communication with said rotatingdetonation combustor such that the flow of cooling air is channeled in asecond direction, opposite from the first direction, within said coolingconduit.
 4. The turbine engine assembly in accordance with claim 1,wherein said cooling conduit extends along said radially inner sidewall, wherein said rotating detonation combustor is configured tochannel the fuel-air mixture in a first direction within said annularcombustion chamber, and wherein said first compressor is coupled in flowcommunication with said rotating detonation combustor such that the flowof cooling air is channeled in the first direction within said coolingconduit.
 5. The turbine engine assembly in accordance with claim 1,wherein said rotating detonation combustor further comprises a fuel-airmixer configured to receive fuel and air to form the fuel-air mixture,said cooling conduit oriented such that the flow of cooling airchanneled therethrough is further channeled towards said fuel-air mixersuch that the fuel-air mixture is formed from the cooling air.
 6. Theturbine engine assembly in accordance with claim 5, wherein said coolingconduit and said fuel-air mixer are coupled in flow communication suchthat the air in the fuel-air mixture is derived entirely from the flowof cooling air.
 7. The turbine engine assembly in accordance with claim1 further comprising a second compressor configured to receive a flow ofbleed air from said first compressor, and configured to discharge a flowof boosted cooling air towards said rotating detonation combustor suchthat the fuel-air mixture is formed from a mixed flow of cooling air andboosted cooling air.
 8. The turbine engine assembly in accordance withclaim 7 further comprising a cooling device positioned between saidfirst compressor and said second compressor, said cooling deviceconfigured to cool the flow of bleed air before being channeled towardssaid second compressor.
 9. A rotating detonation combustor comprising: aradially inner side wall; a radially outer side wall extending aboutsaid radially inner side wall such that an annular combustion chamber isat least partially defined therebetween; and a cooling conduitconfigured to channel cooling air therethrough, said cooling conduitextending along at least one of said radially inner side wall or saidradially outer side wall.
 10. The rotating detonation combustor inaccordance with claim 9 further comprising a plurality of thermallyconductive projection members extending into an interior of said coolingconduit from at least one of said radially inner side wall or saidradially outer side wall.
 11. The rotating detonation combustor inaccordance with claim 9 further comprising: a first end plate coupled tosaid radially inner side wall and said radially outer side wall, saidfirst end plate at least partially defining said annular combustionchamber, wherein said first end plate comprises an air inlet definedtherein; and a second end plate spaced from said first end plate and atleast partially defining said cooling conduit such that the cooling airchanneled therethrough is further channeled towards said air inlet. 12.The rotating detonation combustor in accordance with claim 9 furthercomprising a first annular jacket radially spaced from said radiallyouter side wall such that said cooling conduit is defined between saidradially outer side wall and said first annular jacket.
 13. The rotatingdetonation combustor in accordance with claim 9 further comprising asecond annular jacket radially spaced from said radially inner side wallsuch that said cooling conduit is defined between said radially innerside wall and said second annular jacket.
 14. The rotating detonationcombustor in accordance with claim 9, wherein said cooling conduitextends within a portion of at least one of said radially inner sidewall or said radially outer side wall.
 15. The rotating detonationcombustor in accordance with claim 14, wherein at least a portion ofsaid at least one of said radially inner side wall or said radiallyouter side wall is recessed relative to an interior of said annularcombustion chamber such that a stepped side wall portion is formed, saidstepped side wall portion defining an air pocket within said annularcombustion chamber, and said stepped side wall portion comprising anopening defined therein that couples said cooling conduit in flowcommunication with said air pocket.
 16. A turbine engine assemblycomprising: a rotating detonation combustor configured to combust afuel-air mixture, wherein said rotating detonation combustor comprises:a radially inner side wall; a radially outer side wall extending aboutsaid radially inner side wall such that an annular combustion chamber isat least partially defined therebetween; and a cooling conduit extendingalong at least one of said radially inner side wall or said radiallyouter side wall; and a source of cooling fluid coupled in flowcommunication with said rotating detonation combustor, said source ofcooling fluid configured to discharge a flow of cooling fluid towardssaid rotating detonation combustor, and configured to channel the flowof cooling fluid through said cooling conduit, wherein the cooling fluidincludes at least one of steam, water, or fuel.
 17. The turbine engineassembly in accordance with claim 16, wherein said source of coolingfluid is configured to channel steam or water through said coolingconduit such that heated steam or heated water is formed, said turbineengine assembly further comprising a steam turbine configured to receivea flow of heated steam or heated water from said cooling conduit. 18.The turbine engine assembly in accordance with claim 16, wherein saidsource of cooling fluid is configured to channel fuel through saidcooling conduit, wherein at least one of said radially inner side wallor said radially outer side wall comprises at least one fuel inletdefined therein, said at least one fuel inlet configured to inject thefuel into said annular combustion chamber.
 19. The turbine engineassembly in accordance with claim 18, wherein said at least one fuelinlet comprises a plurality of fuel inlets spaced axially from eachother relative to a centerline of said rotating detonation combustor.20. The turbine engine assembly in accordance with claim 18, whereinsaid rotating detonation combustor further comprises a fuel-air mixerpositioned within said annular combustion chamber upstream from said atleast one fuel inlet relative to a flow direction of the fuel-airmixture.